Trunnion for high-pressure turbine, and turbojet engine including such a trunnion
View Patent ↗The invention relates to a trunnion ( 23 ) for a high-pressure turbine ( 11 ), to be arranged between a shaft of a low-pressure turbine ( 9 ) and an inner surface ( 34 ) of a seal mounting ( 26 ) of the low-pressure turbine ( 8 ), the trunnion ( 23 ) being characterized in that it includes a drop-launching extension ( 32 ) arranged such as to extend opposite a flared portion ( 33 ) of the inner surface ( 34 ) of the seal mounting ( 26 ), such that when the trunnion ( 23 ) is rotated about the shaft of the low-pressure turbine ( 9 ), oil (H 2 ), which tends to penetrate between the trunnion ( 23 ) and the seal mounting ( 26 ), is thrown by centrifugal effect from the drop-launching extension ( 32 ) toward the flared portion ( 33 ) of the inner surface ( 34 ) of the seal mounting ( 26 ).
1. A trunnion for high-pressure turbine, intended to be arranged between a low-pressure turbine shaft and an inner surface of a seal support of a low-pressure turbine, the trunnion comprising a drop-launching extension extending facing a flared portion of the inner surface of the seal support, such that when the trunnion is driven in rotation around the low-pressure turbine shaft, oil is projected by centrifugal effect from the drop-launching extension towards the flared portion of the inner surface of the seal support, the trunnion further comprising a recess arranged in an outer surface of the trunnion, the recess stopping penetration of the oil between the trunnion and the seal support and causing detachment of the oil towards the inner surface of the seal support by centrifugal effect, wherein the drop-launching extension has an outer surface tilted relative to an axis of rotation of the trunnion, to guide the oil towards the recess by centrifugal effect when the trunnion is driven in rotation.
2. The trunnion according to claim 1 , wherein the recess is an annular groove arranged in the outer surface of the trunnion.
3. The trunnion according claim 1 , comprising a series of radial flanges forming a sealing labyrinth between the trunnion and the seal support.
4. A turbojet engine comprising a low-pressure compressor, a high-pressure compressor, a high-pressure turbine and a low-pressure turbine, the turbojet engine further comprising:
a low-pressure turbine shaft connecting the low-pressure compressor to the low-pressure turbine,
a high-pressure compressor shaft extending around the low-pressure turbine shaft, and connecting the high-pressure compressor to the high-pressure turbine,
wherein the low-pressure turbine comprises a seal support presenting an inner surface having a flared portion and the high-pressure turbine comprises a trunnion, disposed between the low-pressure turbine shaft and the inner surface of the seal support of the low-pressure turbine, wherein said trunnion is disposed between the low-pressure turbine shaft and an inner surface of a seal support of the low-pressure turbine, the trunnion including a drop-launching extension extending facing a flared portion of the inner surface of the seal support, such that when the trunnion is driven in rotation around the low-pressure turbine shaft, oil is projected by centrifugal effect from the drop-launching extension towards the flared portion of the inner surface of the seal support, the trunnion further comprising a recess arranged in an outer surface of the trunnion, the recess stopping penetration of the oil between the trunnion and the seal support and causing detachment of the oil towards the inner surface of the seal support by centrifugal effect, wherein the drop-launching extension has an outer surface tilted relative to an axis of rotation of the trunnion, to guide the oil towards the recess by centrifugal effect when the trunnion is driven in rotation.